CN110700964B - Propellant supply system, rocket engine and rocket - Google Patents
Propellant supply system, rocket engine and rocket Download PDFInfo
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- CN110700964B CN110700964B CN201911177436.7A CN201911177436A CN110700964B CN 110700964 B CN110700964 B CN 110700964B CN 201911177436 A CN201911177436 A CN 201911177436A CN 110700964 B CN110700964 B CN 110700964B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/58—Propellant feed valves
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
The invention provides a propellant supply system, a rocket engine and a rocket, and relates to the technical field of gas propulsion devices. The system comprises a propellant supply system, an oxidizer supply system and a control device, wherein a pipeline of the fuel supply system is provided with a first flow regulating valve, and/or a pipeline of the oxidizer supply system is provided with a second flow regulating valve; the first flow regulating valve and the second flow regulating valve are both connected with the control device. When the propellant supply system realizes a large flow regulation ratio, the control device regulates the flow of fuel through the first flow regulation valve and regulates the flow of oxidant through the second flow regulation valve, so that the number of pipelines is greatly reduced, the overall structure can be reduced, and the overall weight is reduced. In addition, since the number of pipes is reduced, the flow path of the fuel or the oxidant is shortened, and the pressure loss of the fuel or the oxidant during the flow is reduced.
Description
Technical Field
The invention relates to the technical field of gas propulsion devices, in particular to a propellant supply system, a rocket engine and a rocket.
Background
In recent years, the development in the aerospace field has placed higher demands on conventional variable thrust rocket engines. In manned lunar landing, Mars detection or deep space detection tasks, the rocket engine needs to work in the injection mode, the sub-combustion/super-combustion mode, the pure rocket mode and other working conditions, the requirements of different working conditions on the thrust of the rocket engine are greatly different, the rocket engine needs to have a large thrust variation range, and the thrust adjustment of the rocket engine is realized through the flow adjustment of the propellant.
The flow regulation of a propellant supply system in the prior art is mainly realized by an injector regulation, a pipeline regulation and the like, wherein the pipeline regulation is mainly realized by connecting a plurality of groups of pipelines in parallel, the regulation condition is good under the condition of small flow change, but the pipeline quantity of the propellant supply system is more and the structure is huge under the condition of large flow regulation ratio (for example, more than 10: 1).
Disclosure of Invention
A first object of the present invention is to provide a propellant supply system to alleviate the technical problem of the prior art that a propellant supply system for adjusting the flow rate through parallel pipelines has a large flow rate adjustment ratio.
The invention provides a propellant supply system, which comprises a fuel supply system, an oxidizer supply system and a control device, wherein a pipeline of the fuel supply system is provided with a first flow regulating valve, and/or a pipeline of the oxidizer supply system is provided with a second flow regulating valve; the first flow regulating valve and the second flow regulating valve are both connected with the control device.
Furthermore, a fuel storage tank, a first flow meter, a first on-off valve and a first one-way valve are arranged on a pipeline of the fuel supply system, and the fuel storage tank, the first flow meter, the first flow regulating valve, the first on-off valve and the first one-way valve are arranged in sequence along the flow direction of fuel;
the first flowmeter is connected with the control device, and the first on-off valve is used for controlling the on-off of a pipeline of the fuel supply system.
Further, the fuel supply system further comprises a pressure increasing device, the pressure increasing device comprises a gas storage tank and a pressure increasing pipeline communicated between the gas storage tank and the fuel storage tank, and the pressure increasing pipeline is sequentially provided with a gas storage tank pressure gauge, a second cut-off valve, a first filter, a first pressure reducer upstream pressure sensor, a first pressure reducer downstream pressure sensor, a third cut-off valve and a second one-way valve along the direction from the gas storage tank to the fuel storage tank;
the upstream pressure sensor of the first pressure reducer and the downstream pressure sensor of the first pressure reducer are both connected with the control device; and the second on-off valve and the third on-off valve are used for controlling the on-off of a pipeline of the fuel supply system.
Further, the fuel tank is provided with a first safety valve and a first relief valve, and/or the gas tank is provided with a second safety valve and a second relief valve.
Further, the first flow regulating valve is an electro-hydraulic servo valve.
Furthermore, an oxidant storage tank pressure gauge, a fourth shutoff valve, a second filter, a second pressure reducer upstream pressure sensor, a second pressure reducer downstream pressure sensor, a second flowmeter, a fifth shutoff valve and a third check valve are further arranged on a pipeline of the oxidant supply system, and along the flow direction of the oxidant, the oxidant storage tank pressure gauge, the fourth shutoff valve, the second filter, the second pressure reducer upstream pressure sensor, the second pressure reducer downstream pressure sensor, the second flowmeter, the second flow regulating valve, the fifth shutoff valve and the third check valve are arranged in sequence;
the upstream pressure sensor of the second pressure reducer and the downstream pressure sensor of the second pressure reducer are both connected with a control device; and the fourth on-off valve and the fifth on-off valve are used for controlling the on-off of a pipeline of the oxidant supply system.
Further, the oxidant storage tank is provided with a third relief valve and a third relief valve.
Further, the second flow regulating valve is a needle regulating valve.
The propellant supply system provided by the invention can produce the following beneficial effects:
compared with the prior art in which a plurality of pipelines are arranged in parallel to adjust the flow, the propellant supply system greatly reduces the number of the pipelines of the fuel supply system and the oxidizer supply system, thereby reducing the overall structure of the propellant supply system, reducing the overall weight of the propellant supply system and further reducing the load of a rocket or enabling the rocket to carry more propellants, finally, the sailing distance of the rocket is prolonged.
The propellant supply system provided by the invention can also be provided with only a first flow regulating valve in the fuel supply system or only a second flow regulating valve in the oxidizer supply system. Compared with the mode of adjusting the flow rate by parallel pipelines in the prior art, the two setting modes respectively realize the reduction of the number of pipelines of the fuel supply system and the reduction of the number of pipelines of the oxidant supply system, thereby reducing the overall structure of the propellant supply system to a certain extent, lightening the overall weight of the propellant supply system, lightening the load of the rocket to a certain extent or enabling the rocket to carry more propellants, and finally prolonging the sailing distance of the rocket.
In addition, as the number of pipelines of the propellant supply system is reduced, and the flow path of the fuel or the oxidant is shortened, the pressure loss of the fuel or the oxidant in the flow process can be reduced, the pressure stability is kept, and the stable operation of the rocket is further favorably maintained; compared with a propellant supply system for adjusting the flow through a parallel pipeline, the propellant supply system provided by the invention adopts the flow adjusting valve to adjust the flow, so that a large flow adjusting ratio can be realized more easily, and the requirements of rockets under different working conditions are met.
A second object of the present invention is to provide a rocket engine to alleviate the technical problem of the prior art that the structure of a propellant supply system for adjusting the flow rate through parallel pipelines is large when the flow rate adjustment ratio is large.
The rocket engine provided by the invention comprises a thrust chamber and the propellant supply system, wherein the propellant supply system is connected with a combustion chamber of the thrust chamber.
The propellant supply system of the rocket engine provided by the invention has all the beneficial effects, so the details are not repeated herein.
A third object of the present invention is to provide a rocket which is capable of alleviating the problem of the prior art that the structure of a propellant supply system for adjusting the flow rate through parallel pipelines is large when the flow rate adjustment ratio is large.
The rocket provided by the invention comprises the rocket engine.
The propellant supply system of the rocket engine of the rocket provided by the invention has all the beneficial effects, so the details are not repeated herein.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic diagram of a propellant supply system in connection with a combustion chamber according to an embodiment of the present invention;
FIG. 2 is a graph of combustion chamber pressure over time during a thermal state validation test of a rocket engine provided in accordance with an embodiment of the present invention.
Icon:
110-a fuel storage tank; 111-a first safety valve; 112-a first bleed valve; 120-a first flow meter; 130-a first flow regulating valve; 140-a first on-off valve; 150-a first one-way valve;
210-a gas storage tank; 211-a second safety valve; 212-a second bleed valve; 220-gas tank pressure gauge; 230-a second on-off valve; 240-a first filter; 250-a pressure sensor upstream of the first pressure reducer; 260-a first stress-reducer; 270-a pressure sensor downstream of the first pressure reducer; 280-a third shutoff valve; 290-a second one-way valve;
310-an oxidant storage tank; 311-a third safety valve; 312 — a third relief valve; 320-oxidant storage tank pressure gauge; 330-fourth shutoff valve; 340-a second filter; 350-a second pressure reducer upstream pressure sensor; 360-a second pressure reducer; 370-a pressure sensor downstream of the second pressure reducer; 380-a second flow meter; 390-a second flow regulating valve; 391-a fifth on-off valve; 392-a third one-way valve;
400-a control device;
500-combustion chamber.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it should be noted that the terms "first", "second", "third", "fourth", "fifth", and the like are used only for distinguishing the description, and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "connected," and "connected" are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
Some embodiments of the invention are described in detail below with reference to the accompanying drawings. The embodiments described below and the features of the embodiments can be combined with each other without conflict.
The present embodiment provides a propellant supply system for supplying a liquid propellant and a gas propellant, as shown in fig. 1, which includes a fuel supply system whose piping is provided with a first flow rate regulation valve 130, an oxidizer supply system whose piping is provided with a second flow rate regulation valve 390, and a control device 400; the first flow rate adjustment valve 130 and the second flow rate adjustment valve 390 are both connected to the control device 400.
The propellant supply system provided by this embodiment, when a large flow regulation ratio is realized, the control device 400 regulates the flow of fuel through the first flow regulation valve 130, and regulates the flow of oxidizer through the second flow regulation valve 390, thereby realizing the flow regulation of the propellant supply system.
In addition, as the number of pipelines of the propellant supply system is reduced, and the flow path of the fuel or the oxidant is shortened, the pressure loss of the fuel or the oxidant in the flow process can be reduced, the pressure stability is kept, and the stable operation of the rocket is further favorably maintained; and, compare in the propellant supply system through parallelly connected pipeline regulated flow, the propellant supply system that this application provided adopts flow control valve to carry out flow control and realizes big flow control ratio more easily to satisfy the demand of rocket under the different operating modes.
In other embodiments of the present application, the propellant supply system may also be provided with only the fuel supply system with the first flow regulating valve 130, or only the oxidizer supply system with the second flow regulating valve 390.
In the present embodiment, the first flow rate adjustment valve 130 may be an electro-hydraulic servo valve, and more specifically, the first flow rate adjustment valve 130 may be a liquid electro-hydraulic servo valve.
In the present embodiment, the second flow rate adjustment valve 390 may be a needle type adjustment valve, and more specifically, the second flow rate adjustment valve 390 may be a gas needle type adjustment valve.
In this embodiment, please continue to refer to fig. 1, a fuel storage tank 110, a first flow meter 120, a first on-off valve 140 and a first check valve 150 are further disposed on a pipeline of the fuel supply system, and along the flow direction of the fuel, the fuel storage tank 110, the first flow meter 120, the first flow regulating valve 130, the first on-off valve 140 and the first check valve 150 are sequentially disposed; the first flow meter 120 is connected to the control device 400, and the first on-off valve 140 is used to control the on-off of the piping of the fuel supply system.
Specifically, the fuel storage tank 110 is used to store liquid fuel, for example, kerosene for a rocket.
Specifically, the first flow meter 120 may be a turbine flow meter.
Specifically, the first on-off valve 140 may be a solenoid valve, and the solenoid valve is connected to the control device 400. The electromagnetic valve is used for controlling the on-off of the pipeline of the fuel supply system, so that the fuel supply system is more timely and efficient. Of course, the first on-off valve 140 may be a manual valve, and the embodiment is not limited thereto.
In this embodiment, with continued reference to fig. 1, the fuel supply system further includes a pressure increasing device, which is used for increasing the pressure of the fuel in the fuel storage tank 110 to keep the fuel at a certain working pressure; the pressure increasing device comprises a gas storage tank 210 and a pressure increasing pipeline communicated between the gas storage tank 210 and the fuel storage tank 110, and the pressure increasing pipeline is sequentially provided with a gas storage tank pressure gauge 220, a second cut-off valve 230, a first filter 240, a first pressure reducer upstream pressure sensor 250, a first pressure reducer 260, a first pressure reducer downstream pressure sensor 270, a third cut-off valve 280 and a second one-way valve 290 along the direction from the gas storage tank 210 to the fuel storage tank 110; both the first pressure reducer upstream pressure sensor 250 and the first pressure reducer downstream pressure sensor 270 are connected to the control device 400; the second cut-off valve 230 and the third cut-off valve 280 are each used to control the opening and closing of the piping of the fuel supply system.
Specifically, the gas storage tank 210 stores nitrogen, i.e., the present embodiment uses nitrogen to pressurize fuel within the fuel storage tank 110. In other embodiments of the present application, the gas storage tank 210 may also store other gases, such as: helium, i.e., helium is used to pressurize the fuel within fuel storage tank 110.
Specifically, the second cut-off valve 230 may be a manual valve, and more specifically, the second cut-off valve 230 may be a manual ball valve.
Specifically, the third on-off valve 280 may be a solenoid valve, which is connected to the control device 400, like the first on-off valve 140. The electromagnetic valve is used for controlling the on-off of the pressurization pipeline, and the advantages of timeliness and high efficiency are also achieved. Of course, the third cut-off valve 280 may be a manual valve, and this embodiment is not limited thereto.
In this embodiment, with continued reference to fig. 1, the fuel tank 110 is provided with a first relief valve 111 and a first relief valve 112, and the gas tank 210 is provided with a second relief valve 211 and a second relief valve 212. The first safety valve 111 plays a role of passive protection, and automatically releases pressure when the pressure in the fuel storage tank 110 exceeds a set pressure, and automatically stops when the pressure in the fuel storage tank 110 is released to the set pressure; the first bleed valve 112 is primarily used during maintenance, and a maintenance person manually opens the first bleed valve 112 as needed to bleed the pressure within the fuel storage tank 110 to a desired pressure. The second relief valve 211 has a similar function and operation principle to the first relief valve 111, and the second relief valve 212 has a similar function and operation principle to the first relief valve 112, so that the details thereof are not repeated herein.
It should be noted that in other embodiments of the present application, only the fuel tank 110 may be provided with the first relief valve 111 and the first relief valve 112, or only the gas tank 210 may be provided with the second relief valve 211 and the second relief valve 212.
In this embodiment, with reference to fig. 1, the pipeline of the oxidant supply system is further provided with an oxidant storage tank 310, an oxidant storage tank pressure gauge 320, a fourth shutoff valve 330, a second filter 340, a second pressure reducer upstream pressure sensor 350, a second pressure reducer 360, a second pressure reducer downstream pressure sensor 370, a second flow meter 380, a fifth shutoff valve 391 and a third check valve 392, and along the flow direction of the oxidant, the oxidant storage tank 310, the oxidant storage tank pressure gauge 320, the fourth shutoff valve 330, the second filter 340, the second pressure reducer upstream pressure sensor 350, the second pressure reducer 360, the second pressure reducer downstream pressure sensor 370, the second flow meter 380, the second flow regulating valve 390, the fifth shutoff valve 391 and the third check valve 392 are sequentially arranged; both the second pressure reducer upstream pressure sensor 350 and the second pressure reducer downstream pressure sensor 370 are connected to the control device 400; the fourth shut-off valve 330 and the fifth shut-off valve 391 are both used to control the on/off of the piping of the oxidant supply system.
Specifically, the oxidant storage tank 310 may store oxygen, i.e., the present embodiment uses oxygen as the oxidant.
Specifically, like the second cut-off valve 230, the fourth cut-off valve 330 may also be a manual valve, and more specifically, the fourth cut-off valve 330 may be a manual ball valve.
Specifically, the second flow meter 380 may be a coriolis flow meter.
Specifically, the fifth on-off valve 391 may be a solenoid valve, which is connected to the control device 400, like the first on-off valve 140 and the third on-off valve 280. The electromagnetic valve is used for controlling the on-off of the pipeline of the oxidant supply system, and the advantages of timeliness and high efficiency are also achieved. Of course, the fifth on-off valve 391 may be a manual valve, which is not limited in this embodiment.
In this embodiment, referring to fig. 1, the oxidant storage tank 310 is provided with a third relief valve 311 and a third relief valve 312. The third relief valve 311 has a similar function and operation principle to the first relief valve 111, and the third relief valve 312 has a similar function and operation principle to the first relief valve 112, so that the detailed description thereof is omitted.
The present embodiment also provides a rocket engine comprising a thrust chamber and a propellant supply system as described above, the propellant supply system being connected to the combustion chamber 500 of the thrust chamber. Through carrying out the hot verification experiment to this rocket engine, can learn that this rocket engine normal operation, and extrusion formula supply system can carry out flow control as required. Fig. 2 is a graph showing the change of the combustion chamber pressure with time in the thermal state verification test of the rocket engine provided in this embodiment. As shown in FIG. 2, the rocket engine realizes normal operation under three working conditions, and the pressure difference of the combustion chamber 500 under the three working conditions is larger, but the transition process from the first working condition to the second working condition and the transition process from the second working condition to the third working condition are more stable. The large change of the pressure of the combustion chamber 500 under different working conditions is realized by the flow regulation of the large flow regulation ratio of the propellant supply system, and the pressure of the combustion chamber 500 is positively correlated with the thrust of the rocket engine, so the propellant supply system of the rocket engine realizes the large change of the pressure of the combustion chamber 500 under different working conditions of the rocket engine through the large flow regulation ratio, and further realizes the thrust regulation in a large range.
Specifically, in the present embodiment, the rocket engine is a variable thrust rocket engine. In the working process of the variable thrust rocket engine, the propellant supply system can adjust the flow of the propellant in real time and correct the flow according to the feedback of each sensor and the like, so that the negative feedback closed-loop adjustment of the flow of the propellant is realized, and the high-precision control of the flow of the propellant is ensured.
Specifically, before the hot verification test, the cold inspection or debugging of the propellant supply system is required, which specifically includes:
with regard to the fuel supply system, the following checks or commissioning needs to be performed:
checking whether the indication number of the gas storage tank pressure gauge 220 is above a set value to ensure that the pressure of the nitrogen in the gas storage tank 210 meets the requirement; if the pressure of the nitrogen in the gas storage tank 210 does not meet the requirement, filling the nitrogen into the gas storage tank 210 until the pressure of the nitrogen in the gas storage tank 210 meets the requirement;
checking whether the level of kerosene in the fuel tank 110 is not less than 20% of the total height of the fuel tank 110 to ensure that the kerosene is sufficient; if the liquid level of the kerosene is too low, the kerosene is supplemented into the fuel storage tank 110 until the liquid level of the kerosene reaches a set liquid level;
and opening a manual ball valve of the pressurization pipeline, enabling the high-pressure nitrogen to flow to the upstream of the first pressure reducer 260, pressurizing the fuel storage tank 110 by checking the upstream pressure sensor 250 of the first pressure reducer and slowly adjusting the first pressure reducer 260, and when the reading of the downstream pressure sensor 270 of the first pressure reducer reaches a set value, finishing pressurization and waiting for a test to be carried out.
With regard to the oxidant supply system, the following checks or commissioning needs to be performed:
checking whether the indication of the oxidant storage tank pressure gauge 320 is above a set value to ensure that the pressure of the oxygen in the oxidant storage tank 310 meets requirements; if the pressure of the oxygen in the oxidant storage tank 310 does not meet the requirement, filling the oxidant storage tank 310 with oxygen until the pressure of the oxygen in the oxidant storage tank 310 meets the requirement;
the manual ball valve of the pipeline of the oxidant supply system is opened, the high-pressure oxygen flows to the upstream of the second pressure reducer 360, the reading of the second pressure reducer downstream pressure sensor 370 can reach the design value by checking the second pressure reducer upstream pressure sensor 350 and adjusting the second pressure reducer 360, and the test is waited for.
After the inspection and the debugging are completed, a thermal state verification test is performed, and in the test process, the control device acquires information of the first pressure reducer upstream pressure sensor 250, the first pressure reducer downstream pressure sensor 270, the second pressure reducer upstream pressure sensor 350, the second pressure reducer downstream pressure sensor 370, the first flow meter 120 and the second flow meter 380, and controls the first flow regulating valve 130, the first on-off valve 140, the third on-off valve 280, the second flow regulating valve 390 and the fifth on-off valve 391 according to the acquired information. In the flow rate adjustment of the fuel, the value of the first flow meter 120 is input, and the operation of the first flow rate adjustment valve 130 is output; in the flow rate adjustment of the oxidizing agent, the value of the pressure sensor 370 downstream of the second pressure reducer is input, and the operation of the second flow rate adjustment valve 390 is output.
The embodiment also provides a rocket which comprises the rocket motor.
The rocket provided by the embodiment has all the beneficial effects of the rocket engine, and therefore, the details are not described herein.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. A propellant supply system, characterized by comprising a fuel supply system, an oxidizer supply system and a control device (400), the piping of the fuel supply system being provided with a first flow regulating valve (130), the piping of the oxidizer supply system being provided with a second flow regulating valve (390); the first flow control valve (130) and the second flow control valve (390) are both connected to the control device (400);
a first flow meter (120) connected with the control device (400) is further arranged on the pipeline of the fuel supply system, and a second flow meter (380) connected with the control device (400) is further arranged on the pipeline of the oxidant supply system;
the first flow meter (120) is used for monitoring the fuel supply system pipeline flow, the second flow meter (380) is used for monitoring the oxidant supply system pipeline flow, and the control device (400) is used for receiving monitoring information of the first flow meter (120) and the second flow meter (380) and simultaneously adjusting the flow sizes of the first flow regulating valve (130) and the second flow regulating valve (390) in real time according to the detected information;
the control device (400) is matched with the first flow meter (120) and the second flow meter (380) to adjust the first flow regulating valve (130) and the second flow regulating valve (390) in real time so as to adjust the flow size in a single continuous experiment process;
the fuel supply system is used for supplying liquid fuel, and the oxidant supply system is used for supplying gas oxidant.
2. The propellant supply system according to claim 1 wherein a fuel storage tank (110), a first on-off valve (140) and a first check valve (150) are further provided on the piping of the fuel supply system, and the fuel storage tank (110), the first flow meter (120), the first flow rate adjustment valve (130), the first on-off valve (140) and the first check valve (150) are provided in this order in the flow direction of fuel;
the first on-off valve (140) is used for controlling the on-off of a pipeline of the fuel supply system.
3. The propellant supply system of claim 2 further comprising a pressure boosting device comprising a gas tank (210) and a pressure boosting line communicating between the gas tank (210) and the fuel tank (110), and having a gas tank pressure gauge (220), a second shut-off valve (230), a first filter (240), a first pressure reducer upstream pressure sensor (250), a first pressure reducer (260), a first pressure reducer downstream pressure sensor (270), a third shut-off valve (280), and a second one-way valve (290) disposed in that order along the pressure boosting line from the gas tank (210) to the fuel tank (110);
said first pressure reducer upstream pressure sensor (250) and said first pressure reducer downstream pressure sensor (270) are both connected to said control device (400); the second on-off valve (230) and the third on-off valve (280) are used for controlling the on-off of a pipeline of the fuel supply system.
4. Propellant supply system according to claim 3, characterized in that the fuel tank (110) is provided with a first safety valve (111) and a first relief valve (112) and/or the gas tank (210) is provided with a second safety valve (211) and a second relief valve (212).
5. Propellant supply system according to any of claims 1-4, characterized in that the first flow regulating valve (130) is an electro-hydraulic servo valve.
6. The propellant supply system of claim 1 wherein the oxidizer supply system further comprises an oxidizer tank (310), an oxidizer tank pressure gauge (320), a fourth shutoff valve (330), a second filter (340), a second pressure reducer upstream pressure sensor (350), a second pressure reducer (360), a second pressure reducer downstream pressure sensor (370), a fifth shutoff valve (391), and a third check valve (392) disposed in piping, and wherein the oxidizer tank (310), the oxidizer tank pressure gauge (320), the fourth shutoff valve (330), the second filter (340), the second pressure reducer upstream pressure sensor (350), the second pressure reducer (360), the second pressure reducer downstream pressure sensor (370), the second flow meter (380), and a third check valve (392) are disposed along the flow direction of the oxidizer, The second flow regulating valve (390), the fifth on-off valve (391) and the third check valve (392) are arranged in sequence;
the second pressure reducer upstream pressure sensor (350) and the second pressure reducer downstream pressure sensor (370) are both connected to a control device (400); the fourth on-off valve (330) and the fifth on-off valve (391) are used for controlling the on-off of a pipeline of the oxidant supply system.
7. Propellant supply system according to claim 6, characterized in that the oxidizer tank (310) is provided with a third safety valve (311) and a third relief valve (312).
8. Propellant supply system according to claim 1, 6 or 7, characterized in that the second flow regulating valve (390) is a needle regulating valve.
9. A rocket engine comprising a thrust chamber and a propellant supply system according to any one of claims 1 to 8, said propellant supply system being connected to a combustion chamber (500) of said thrust chamber.
10. A rocket comprising the rocket engine of claim 9.
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| CN201911177436.7A CN110700964B (en) | 2019-11-25 | 2019-11-25 | Propellant supply system, rocket engine and rocket |
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| CN201911177436.7A CN110700964B (en) | 2019-11-25 | 2019-11-25 | Propellant supply system, rocket engine and rocket |
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| CN112253336B (en) * | 2020-09-09 | 2021-12-07 | 北京航天动力研究所 | Test system for verifying flameout boundary of combustion device and flameout boundary determining method |
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